Code Development to Determine the Temperature from the OH* Chemiluminescence Recordings in a Supersonic Combusting Flow

Paper


Sopek, Tamara, Brieschenk, Stefan, Lorrain, Philippe, McIntyre, Timothy J. and Boyce, Russell R.. 2014. "Code Development to Determine the Temperature from the OH* Chemiluminescence Recordings in a Supersonic Combusting Flow." 45th AIAA Plasmadynamics and Lasers Conference (2014). Atlanta, United States 16 - 20 Jun 2014 United States. https://doi.org/10.2514/6.2014-2243
Paper/Presentation Title

Code Development to Determine the Temperature from the OH* Chemiluminescence Recordings in a Supersonic Combusting Flow

Presentation TypePaper
AuthorsSopek, Tamara (Author), Brieschenk, Stefan (Author), Lorrain, Philippe (Author), McIntyre, Timothy J. (Author) and Boyce, Russell R. (Author)
Journal or Proceedings TitleProceedings of the 45th AIAA Plasmadynamics and Lasers Conference (2014)
Number of Pages11
Year2014
Place of PublicationUnited States
ISBN9781624102905
Digital Object Identifier (DOI)https://doi.org/10.2514/6.2014-2243
Web Address (URL) of Paperhttps://arc.aiaa.org/doi/abs/10.2514/6.2014-2243
Conference/Event45th AIAA Plasmadynamics and Lasers Conference (2014)
Event Details
45th AIAA Plasmadynamics and Lasers Conference (2014)
Parent
AIAA Plasmadynamics and Lasers Conference
Event Date
16 to end of 20 Jun 2014
Event Location
Atlanta, United States
Abstract

Experimental investigations of scramjet combustion are the focus of experimental studies performed in T4 facility at The University of Queensland. The objective of the present study is to develop code support to determine OH temperatures in such high speed flows. For this purpose available source codes, namely SPARTAN and Photaura, had to be extended in order to include OH species in their databases. Validation of the OH modelling in SPARTAN and Photaura was done by comparison with the results of LIFBASE simulations. The results of these codes were compared with the OH* chemiluminescence spectra obtained using a Mach 9 enthalpy-equivalent flight condition. A two-dimensional scramjet model with a constant-area supersonic combustor was used in the experimental investigation. The OH* chemiluminescence signal was recorded and the spectrally resolved measurements of the OH* emission spectra have been conducted in order to characterise the ignition and combustion processes. When compared with the spectrally resolved OH* emission spectra, the results of spectral simulations demonstrate a very good agreement. The comparison with the experimental data indicate that results of three synthetic spectral simulation can be considered as a consistent representation of the physical phenomena and can serve as a pre-experiment indication of the combustion process studied. The presented results show the possibility of using OH* chemiluminescence spectra to infer relative temperatures in supersonic combustion. Absolute temperatures can be inferred if the offset between the intensity-versus-temperature functions for OH* and OH is known.

KeywordsCombustion pro-cess; Experimental investigations; Relative temperatures; Spectral simulations; Supersonic combustion; Supersonic combustors; Temperature function; University of Queensland
ANZSRC Field of Research 2020400106. Hypersonic propulsion and hypersonic aerothermodynamics
401205. Experimental methods in fluid flow, heat and mass transfer
510203. Nonlinear optics and spectroscopy
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Byline AffiliationsUniversity of Queensland
University of New South Wales
Institution of OriginUniversity of Southern Queensland
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